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KM Prespektiva

This project is aimed to demonstrate the performance and weight gains that can be accomplished through the use of fibre steering in laminated composite panels for wing applications produced by automated fibre placement technology. For this purpose, two geometries are selected to resemble the bottom and top wing surfaces; a simple square panel under compressive load resembles the top surface and a rectangular panel with repetitive access holes under tensile and shear load resembles the bottom surface.  The compressive panel is designed to have the maximum buckling load with consideration of stiffness and strength constraints and the tensile panel is designed for maximum failure load. To evaluate the improvements of the optimum steered panels, two baseline panels with optimum straight fibres and quasi-isotropic laminates are also designed and compared. To compare different manufacturing technologies, the panels are manufactured in two ways; thermoset prepreg carbon fibre placement and placement of dry fibre-tows followed by resin infusion. The manufactured panels are C-scaned, trimmed and tested to verify the steering technology improvements.

 


KM Perspektiva I: Fibre Steering, September 2011 - January 2012

Description: This project was part of Russian superjet program. To investigate the potential of steering technology, three square panels under compression ressembling the top surface of the wing were designed; Quasi-Isotropic straight fibre, optimum straight fibre and optimum steered fibre laminates. These panels were optimised for buckling, stiffness and strength performance. The panels were manufacturing with Automated fibre placement using prepreg thermoset materials and once using dry fibres. These panels were experimentally tested in Russia and comparision approved the potential of steering.

 

funded by: ApATeCH‑ Applied Advanced Technology Company Ltd.  and Aerocomposites,

manufacturing subcontract with: NLR and Light weight structures

testing with: TsAGI – Central Aerohydrodynamic Insitute National Composite Center

 


KM Perspektiva II: Optimum Strength Design of Tension Panels with a Hole, February 2012 - July 2012

 

Description: This project was also a part of Russian superjet program and continuation of KM Perspektiva I. Here three rectangular panels with repeating cut-outs, ressembling the access holes in the bottom surface of the wing, were designed under tension. The straight and steered panels were optimised for material strength. The panels were manufacturing with Automated fibre placement using prepreg thermoset materials and will be experimentally tested in Russia.

 

funded by: ApATeCH‑ Applied Advanced Technology Company Ltd.  and Aerocomposites,

manufacturing subcontract with: NLR and Light weight structures

testing with: TsAGI – Central Aerohydrodynamic Insitute National Composite Center

  


 

 

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